Pneumatic airborne ejection system for aerospace vehicles

• US 6,260,802 B1
• Filed: 04/25/2000
• Issued: 07/17/2001
• Est. Priority Date: 04/25/2000
• Status: Expired due to Fees

• Current Assignee: Air Force Government of The United States of America As Represented By The Secretary
• Original Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Inventors: Hampsten, Kenneth R.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/558,456
• Time in Patent Office: 448 Days
• Field of Search: 244/13, 244/46, 244/49, 244/63, 244/137.1, 244/3-4-, 89/18-5-
• US Class Current: 244/137.1
• CPC Class Codes: B64D 1/00 Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight with respect to weapon sights devices F41G takes precedence, parachutes per se B64D17/00; ejectable seats B64D25/10; ejectable capsules B64D25/12; refuelling during flight B64D39/00; launching apparatus for projecting projectiles or missiles F41F1/00, F41F7/00; rocket or torpedo launchers F41F3/00
• CPC Class Codes: B64D 1/08 the articles being load-carrying devices
• CPC Class Codes: B64D 7/08 Arrangements of rocket launchers or releasing meansrocket launchers per se, e.g. rocket pods, F41F3/06
• CPC Class Codes: B64G 1/005 Air launch

Abstract

An airborne pneumatic launch tube ejection system to described for launching an aerospace vehicle/payload into orbit. The system can be installed in a jet transport aircraft without requiring structural modifications.

Claims

1. An airborne aerospace vehicle launch system comprised of:

a. a pneumatic launch tube positioned in an airplane cargo bay containing an aerospace vehicle/payload system, said aerospace vehicle employing storable propellants;

b. modified airplane cargo doors whereby said launch tube extends unobstructed through said modified doors;

c. an inflatable/deflatable contoured bellows plug for filling the aft end of said launch tube, thereby maintaining the aircraft'"'"'s exterior aerodynamic mold lines;

d. a sabot for sealing and supporting said aerospace vehicle/payload system within said tube;

e. a source of high pressure gas capable of expelling said aerospace vehicle from said tube;

f. a jet-air levitation system for floating said aerospace vehicle in said tube at the time of loading the aerospace vehicle into the tube and at the time of ejecting the aerospace vehicle from the tube;

g. a variable geometry, scissor-wing aerodynamic upper and lower lifting surface attached to said aerospace vehicle capable of being stowed in said tube prior to launch and deployed subsequent to launch; and

h. computer means for monitoring and sequencing operations of said airborne satellite aerospace vehicle launch system.

2. The airborne aerospace vehicle launch system of claim 1, wherein said high-pressure gas source is a gas generator.

3. An airborne aerospace vehicle launch system comprised of:

a. a pneumatic launch tube positioned in an airplane cargo bay containing an aerospace vehicle/payload system, said aerospace vehicle employing a cryogenic oxidizer and a storable fuel;

b. modified airplane cargo doors whereby said launch tube extends unobstructed through said modified doors;

c. an inflatable/deflatable contoured bellows plug for filling the aft end of said launch tube, thereby maintaining the aircraft'"'"'s exterior aerodynamic mold lines;

d. a tank external to said launch tube to hold said aerospace vehicle'"'"'s storable propellant;

e. means to transfer said storable propellant to said aerospace vehicle prior to launch;

f. a muzzle door located near the aft end of said launch tube capable of being positioned to close off and seal said tube and of being rapidly withdrawn so said tube is not obstructed at time of launch;

g. a pressure maintenance system capable of pulling a vacuum from said launch tube when sealed by said muzzle door and capable of equalizing the pressure of said tube with the ambient pressure;

h. a sabot for sealing and supporting said aerospace vehicle/payload system;

i. a source of high pressure gas capable of expelling said aerospace vehicle from said tube;

j. a jet-air levitation system for floating said aerospace vehicle in said tube at the time of loading the aerospace vehicle into the tube and at the time of ejecting the aerospace vehicle from the tube;

k. a variable geometry, scissor-wing aerodynamic upper and lower lifting surface attached to said aerospace vehicle capable of being stowed in said tube prior to launch and deployed subsequent to launch; and

l. computer means for monitoring and sequencing operations of said airborne aerospace vehicle launch system.

4. The airborne aerospace vehicle launch system of claim 3, wherein said high-pressure gas source is a gas generator.